27244 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations 

inability to use the remaining fuel supply in 

the inner tank. A short-circuit could also 

result in an ignition source in a flammable 

leakage zone]. 

* * * * * 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Actions 

(g) Within 30 months after the effective 

date of this AD, install Teflon bushes in the 

hydraulic reservoir panel at the lower lefthand side in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–24–6102, 

Revision 01, dated September 24, 2010. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(h) Actions done before the effective date 

of this AD in accordance with Airbus 

Mandatory Service Bulletin A300–24–6102, 

dated August 13, 2009, are acceptable for 

compliance with the corresponding 

requirements of this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(i) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to Attn: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 227–2125; fax (425) 

227–1149. Information may be e-mailed to: 

9-ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

Related Information 

(j) Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2010–0225, 

dated November 5, 2010; and Airbus 

Mandatory Service Bulletin A300–24–6102, 

Revision 01, dated September 24, 2010; for 

related information. 

Material Incorporated by Reference 

(k) You must use Airbus Mandatory 

Service Bulletin A300–24–6102, Revision 01, 

dated September 24, 2010, to do the actions 

required by this AD, unless the AD specifies 

otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Airbus SAS–EAW 

(Airworthiness Office), 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; e-mail account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on April 26, 

2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–10817 Filed 5–10–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0706; Directorate 

Identifier 2010–NM–064–AD; Amendment 

39–16683; AD 2011–10–02] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–400, 747–400D, 

and 747–400F Series Airplanes 

Equipped With General Electric CF6– 

80C2 or Pratt & Whitney PW4000 

Series Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD requires 

modifying certain thrust reverser control 

system wiring to the flap control unit 

(FCU). This AD was prompted by a 

report of automatic retraction of the 

leading edge flaps due to indications 

transmitted to the FCU from the thrust 

reverser control system during takeoff. 

We are issuing this AD to prevent 

automatic retraction of the leading edge 

flaps during takeoff, which could result 

in reduced climb performance and 

consequent collision with terrain and 

obstacles or forced landing of the 

airplane. 

DATES: This AD is effective June 15, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of June 15, 2011. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; or in person at the 

Docket Management Facility between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Tung Tran, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6505; fax 425–917–6590; e-mail: 

tung.tran@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to the 


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Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations 27245 

specified products. That NPRM 

published in the Federal Register on 

August 5, 2010 (75 FR 47245). That 

NPRM proposed to require modifying 

certain thrust reverser control system 

wiring to the flap control unit (FCU). 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Support for the NPRM 

Boeing, Airline Pilots Association, 

International (ALPA), and Japan 

Airlines International (JAL) support the 

intent of the NPRM. 

Requests To Use Latest Service 

Information 

JAL and All Nippon Airways (ANA) 

requested that we update the NPRM to 

reference Boeing Special Attention 

Service Bulletin 747–78–2183, Revision 

1, dated December 23, 2010. The 

commenters stated that Boeing has 

issued Boeing Service Bulletin 

Information Notice 747–78–2183 IN 01, 

dated May 6, 2010, to correct the 

operational test procedure. The NPRM 

referred to Boeing Special Attention 

Service Bulletin 747–78–2183, dated 

January 12, 2010. 

We agree to reference the latest 

service information and have changed 

paragraph (h) of this AD to reference 

Boeing Special Attention Service 

Bulletin 747–78–2183, Revision 1, dated 

December 23, 2010. We have also 

changed paragraph (g) of this AD to 

reference Boeing Alert Service Bulletin 

747–78A2184, Revision 1, dated 

December 23, 2010, which was also 

revised (the NPRM referred to Boeing 

Alert Service Bulletin 747–78A2184, 

dated January 12, 2010). Changes to 

these service bulletins include changes 

to the functional test tasks to better 

describe the use of pneumatic and 

electrical power, and to provide a better 

sequence of test tasks. 

We have also added paragraph (i) to 

this AD to give credit to operators for 

accomplishing the actions specified in 

Boeing Special Attention Service 

Bulletin 747–78–2183 and Boeing Alert 

Service Bulletin 747–78A2184, both 

dated January 12, 2010. We have reidentified subsequent paragraphs 

accordingly. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously— 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of the AD. 

Costs of Compliance 

We estimate that this AD affects 98 

airplanes of U.S. registry. We estimate 

that it will take 1 work-hour per product 

to comply with this AD. The average 

labor rate is $85 per work-hour. 

Required parts would cost $0 per 

product. Based on these figures, we 

estimate the cost of this AD to the U.S. 

operators to be $8,330, or $85 per 

product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2011–10–02 The Boeing Company: 

Amendment 39–16683; Docket No. 

FAA–2010–0706; Directorate Identifier 

2010–NM–064–AD. 

Effective Date 

(a) This AD is effective June 15, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 747–400, 747–400D, and 

747–400F series airplanes; certificated in any 

category; equipped with General Electric 

CF6–80C2 series engines or Pratt & Whitney 

PW4000 series engines, as applicable. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 78: Engine exhaust. 

Unsafe Condition 

(e) This AD was prompted by a report of 

automatic retraction of the leading edge flaps 

due to indications transmitted to the flap 

control unit (FCU) from the thrust reverser 

control system during takeoff. The Federal 

Aviation Administration is issuing this AD to 

prevent automatic retraction of the leading 

edge flaps during takeoff, which could result 

in reduced climb performance and 

consequent collision with terrain and 

obstacles or forced landing of the airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Modification 

(g) For Model 747–400 and –400F airplanes 

equipped with Pratt & Whitney Model 

PW4000 series engines: Within 36 months 


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27246 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations 

after the effective date of this AD, modify the 

thrust reverser control system wiring to the 

FCU in the P252 and P253 thrust reverser 

relay panels, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–78A2184, Revision 1, 

dated December 23, 2010. 

(h) For Model 747–400, –400D, and –400F 

airplanes equipped with General Electric 

Model CF6–80C2 series engines: Within 36 

months after the effective date of this AD, 

modify the thrust reverser control system 

wiring to the FCU in the P414 and P415 

power distribution panels, in accordance 

with Boeing Special Attention Service 

Bulletin 747–78–2183, Revision 1, dated 

December 23, 2010. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(i) Modifying the thrust reverser control 

system wiring before the effective date of this 

AD, in accordance with Boeing Special 

Attention Service Bulletin 747–78–2183 or 

Boeing Alert Service Bulletin 747–78A2184, 

both dated January 12, 2010, as applicable, is 

acceptable for compliance with the 

corresponding modification required by 

paragraph (g) or (h) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

Related Information 

(k) For more information about this AD, 

contact Tung Tran, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; phone: 425–917–6505; fax: 425–917– 

6590; e-mail: tung.tran@faa.gov. 

(l) For information about AMOCs, contact 

Tung Tran, Aerospace Engineer, Propulsion 

Branch, ANM–140S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; phone: 

425–917–6505; fax: 425–917–6590; e-mail: 

tung.tran@faa.gov. 

Material Incorporated by Reference 

(m) You must use Boeing Special Attention 

Service Bulletin 747–78–2183, Revision 1, 

dated December 23, 2010; or Boeing Alert 

Service Bulletin 747–78A2184, Revision 1, 

dated December 23, 2010; as applicable; to do 

the actions required by this AD, unless the 

AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information under 5 U.S.C. 552(a) 

and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; e-mail me.boecom@boeing.com; 

Internet https://www.myboeingfleet.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on April 20, 

2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–10692 Filed 5–10–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1273; Directorate 

Identifier 2010–NM–089–AD; Amendment 

39–16686; AD 2011–10–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310–203, –204, –222, –304, –322, and 

–324 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

A specific area, the lower tail plane cut-out 

located in the tail cone is subject to an 

inspection programme [for cracking] * * *. 

* * * * * 

The unsafe condition is reduced 

structural integrity of the tail cone. We 

are issuing this AD to require actions to 

correct the unsafe condition on these 

products. 

DATES: This AD becomes effective June 

15, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 15, 2011. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on January 3, 2011 (76 FR 46). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

A specific area, the lower tail plane cut-out 

located in the tail cone is subject to an 

inspection programme specified in the 

Airbus Service Bulletin (SB) A310–53–2074. 

EASA issued AD 2007–0053 [which 

superseded French AD 1992–106–132 R6; 

French AD 1992–106–132 corresponds to 

FAA AD 98–26–01] to require the 

accomplishment of this SB at Revision 03. 

Airbus has established that this SB needed 

to be revised in order to state correct 

threshold and intervals due to errors 

introduced at revision 03. Consequently, 

revision 04 of this SB has been issued, and 

opportunity was taken: 

—To clarify the inspection area and 

associated threshold and intervals 

—To take aeroplane utilisation into 

consideration, in accordance with the 

A310 life extension programme. 

For the reasons stated above, this EASA 

AD takes over the requirements of paragraph 

1.16 of EASA AD 2007–0053R1 [currently at 

R3], which has been revised accordingly, and 

requires accomplishment of the instructions 

contained in Airbus SB A310–53–2074 at 

Revision 04. 

The unsafe condition is reduced 

structural integrity of the tail cone. The 

required actions include repetitive and 

one-time inspections, depending on the 

area, of the lower tail plane cut-out, and 

corrective actions if necessary. The 

inspections include the following: 


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